Start pump and generator
AssigneeHamilton Sundstrand Corporation
InventorsEdward Goy, Myles Kelly
Life of this patent
Estimating the term…
Abstract
A fuel system for an aircraft includes a main fuel pump, a metering valve fluidly connected to the main fuel pump, a selector valve fluidly connected to the metering valve, a check valve fluidly connected to the metering valve, and an electric motor driven start pump fluidly connected to the check valve and the selector valve. During a start-up condition, the fuel system is configured to permit a fuel to flow through the electric motor driven start pump and through the selector valve to an engine. During a cruise condition, the fuel system is configured to permit the fuel to flow from a high-pressure fuel source and through the electric motor driven start pump start pump to drive the electric motor driven start pump to generate electrical energy.
Claims20
A fuel system for an aircraft, the fuel system comprising:
- a main fuel pump;
- a metering valve fluidly connected to the main fuel pump;
- a selector valve fluidly connected to the metering valve;
- a check valve fluidly connected to the metering valve;
- and
- an electric motor driven start pump fluidly connected to the check valve and the selector valve;
- wherein during a start-up condition, the fuel system is configured to permit a fuel to flow through the electric motor driven start pump and through the selector valve to an engine;
- and
- wherein during a cruise condition, the fuel system is configured to permit the fuel to flow from a fuel source and through the electric motor driven start pump to drive the electric motor driven start pump to generate electrical energy.
A fuel system for an aircraft, the fuel system comprising:
- a main fuel pump configured to provide a fuel to an engine of the aircraft;
- a start pump configured to provide the fuel to an engine of the aircraft, the start pump being an electric motor driven start pump that is connected to a generator;
- a metering valve fluidly connected to the main fuel pump;
- a selector valve fluidly connected to the metering valve and the start pump and configured to receive the fuel pumped from the main fuel pump and the fuel pumped from the start pump;
- and
- a check valve between the metering valve and the start pump, wherein the check valve is configured to permit a bypass flow to flow from the metering valve to the start pump;
- wherein the start pump is configured to operate in a forward direction to deliver the fuel to the engine of the aircraft during engine start-up and is configured to operate in a reverse direction after engine start-up to generate electrical power.
Dependencies are inferred from the claim text.